Turbo-pump.



G. B. COLLIER.

TURB()4 PUMP.

APPLIDATIOF FILED JAN. 28, 1907.

, Patented Oct. 13, 1908. a sums-enum 1.

l 11m/anunmnmm G. B. GULLIEB. 'y TURBO PUMP. A rrLIuu-Iol funn Ju. as, 1m. l

-Patented Oct. 13,1908

s Bumm 1n:

GY B. COLLIER, 0F KINDERHOK, NW YORK.

TURBO-FUI?.

Bpecicatlon of Lettera Patent.

Patented Oct. 13, 1908.

Appiimm mui Jimmy as, 1907. sei-iai' No. 354,363.

To all whom 'it may concern: Beit known that I,- GUY B. COLLIER, citizen of the United States, and resident of Kinderhook, Columbia county, New York, have invented certain new and useful Imroveinents in Turbo-Pumps, of which the ollowingis a specification.

The invention relates more especially .Ito

\ turbo-pumps'for fluids either gaseous or liqthe motors.

uid although certain features may bodied in .steam` or other elastic fluid `tiirbine Inrpracticing -the various features of the invention in turbo-pum s the :entering fluid is acted upon by rotor b ades the velocity of which increases in successive stages u to the highest blade velocity. In assing t rough vthe rotor blades of a stage t e absolute velocit of the fluid is increased to such a value as will enable Ithean les of the blades in the succeeding stage to e'the most desirable. The fluid 1n passing from one series of rotor blades Vto the .other passes vthro h stator blades which may be so arranged tM t some change in velocity, and in the case of a compressor pump some compression-,lis effected in the guides. It is preferred however to arra'ng'e the guides so that substantially no change' in velocity or pressure is effected therein since this arrangement of guides enables the rotor blades to be more advantageously arr cient action. ith .i the stator blades arranged to act merelyas. guides substantially all change in absolute velocity and in pres'- sure takes place inthe rotorl blades which is of` advantage in that itenables the roter to be driven at a lower rate'of s edand also enables the guides and rotor b ades to be ar ranged at the most desirable angles with relation to each other. By arranging the rotor blades at the entrance end of the pump. so that` the velocity of the blades increases in successive st s the comparatively slow movin fluid is admitted to the comparaf tivel s ow moving blades and the velocit of uid is graduall built up s that w en the iluid arrives at t e oint where the blade velocity isthe highest t e velocit of the fluid may be such as is suitable for t e most advantageous arranglement of the blade angles.

In practicing t e invention in a turboair or other elastic built up in 4the manner -descn through successive series of rotor andV stator ed and results in a more eiiiblades where it is further compressed while the absolute and axial' velocityremains substantially constant 'in successive stages. In

this part of the compressor the blades arev preferably arr edm such manner that vsubstaritiall all t e com ression ta'kesplace in the-rotor lades since t enables the most Vdesirable blade angles to be employed andl enables the compression to be effected in fewer stages. The blades in this part of the rotor ma be arranged so that compression will be e ected inboth the rotor blades and the stator blades but such an arrangement will require more stages`for the same compression and less desirable blade angles. In either case the gradual building up ofthe velocity of the lluid at the entrance end of the compressor in 'the manner heretofore ex-A plained enables the bringing of the fluid.to such a condition as to ve o'cit and pressure when it reaches the point speed is the highest, that a large amount of work per stage may be performed upon it: under the most desirable conditions as to blade angle relations and speedof rotation.

In case it .is desired to deliver the fluid from the pump at a com aratively low velocity the rotor is provi ed at its delivery end with rotor and stator blades arranged to reduce the absolute and axial velocities of the fluid. This result is effected' by increasing the cross sectional area of the passages through which the fluid passes in successive stages. In this part ofthe rotor the speed of the rotor blades decreases iii successive `s while the cross sectional area of the y between the blades in each sta increases from the entrance' side of the bla e to the exit side, the increase referably being more pronounced in the gui e blades. The absolute and axial velocities of the fluid are thus decreased while in the case of an elastic fluid compression takes lace in both the rotor blades and stator bla es. Thereduction in velocity in the stator blades causes the fluid to enter the succeeding lower speed rotor bladesat a speed suitable for the most advantageous arrangement of blade angles. '105 The various features of the invention will be readily understood from the foregoing and from the following detailed description of a turbo-compressor pump illustrated in the accom anying drawings which embodies all the eaturee of the invention in the form in which I prefer to use them;

In the drawings-Figure 1 is a sectional erethe blade view illustrating the turbo-compressor; Fig. 2 is a diagrammatic view illustrating the .arrangement of .the delivery guide blades. Figs. 3 and 4 are views showin the arrangements of the stator androtor lades from A to C in Fig. 1. Figs. `5 and 6 yare views showin the arra ement of ,stator and rotor blades rom Dto in Fig. 1'. Figs. 7, 8 and 9 are views showing an, arrangement -of .blades for a steam turbine embod ing cer'- tain'features of the invention; and `ig. 10 is a view showing the arrangement of blades for a liquid pump embodying certain 4ifea-l tures of the inventlon. v. j As illustrated in the drawings the rotor of the com lressor comprises two drums y1 and 2 secure to and supported by the shafts 3,

8 and in passing from one casing to the p1 e other the fluld ma if desired be' passed through an intercoo er. The casings 6 and 7 may be provided with water jackets in Acaseit is desired to deliver the air at a low temperature.

At the inlet end of the com ressor the rotor drum 1 is so constructed t at its periphe gradually increases in diameter from the iiilet end toward the outlet end andthe blades are so pro ortioned that thevmean velocity of the bla es increases in successive series. In other wordsl the mean velocity of4 the Afirst series of rotor blades'9 is less than the mean velocity of the succeedin series of rotor blades 10 and the velocit of t e bladesl progressively increases in t e successive stages fora certain distance which will vary according to the results which it is desired to accomplish. The casing ,6 is provided with entrance ide blades 11 arranged to admit the liuifutoA the rotor 4blades 9 at a favorable angle and without shock upon the irst series of blades. f

In the construction showny the rotor blade speed in successive stages increases from A to B. The comparatively slow moving air is admitted to the blades 9 which have the lowest velocity and as the fluid passes from A to B the fluid is compressed and the absolute velocity'of the air is increased to the value desired where the blade speed is the highest. To accomplish this the axial clear cross-sectional area (i. e. the area in a plane vat light'angles to the axis) of the .passages through the rotor blades in each stage varies cross-sectional area is less at the outlet than it is at the inlet side of the blades as indicated in Fig. 3. Com ression and change in velocit y thereforeta es place in the rotor blades. l

T e sectional area ofA the passages through the stator bladev at right anglesto the direction of the flow through the passages in each stage may be varied from inlet to exit so that the velocity of the -liuid passing through the Iguide blades will be reduced `to some extent and some comfress'ion be'veflected in the guide blades. t is preferred however .to

make the cross-sectional area of the passages through the guide blades at right angles to the direction of the flow through said pas# sages in each stage substantially uniform from inlet to exit as indicated in Figs. 1 and 3 so that substantially all the com ression and change in velocity is effected in tlie moving rotor blades and this arrangement of stator and rotor blades forms one of the features of the invention. This arrangement enables the use of the most desirable blade angles and angles which will enable a large amount of work to be performed per stage thus reducing the number of stages required.

The variation in the axial clear cross-secprovided for in any suitable manner butV I prefer to eHect the variation by a change in the radial depth of the passages as indicated in Fig. 1 of the drawing and also by change in -the distance between the faces of adjacent blades as indicated in Figs. 3 to 6.

With the inlet end of the com ressor constructed as above described litt echange in the inlet angles a of the blades is required from A to B While the outlet angles b of the blades should be decreased by suitable they should be decreasedin successive stages, or in other Words, the inlet angles should be substantiall the same in successive st es or should A ecrease. The inlet and out et `angles of the guide blades shouldalso beidecreased by suitable amounts at proper stages kamounts as indicated in Fig. 3 to secure the best results. If the inlet angles are changed 110,

in order to secure the greatest amount of work. upon the fluid in each stage.

With the inlet end of the compressor coni structed and arranged as above described the iluid when it reaches the highest rotor blade speed at B is in such a state thata large amount of Work per stage may be performed upon it under the most desirable conditions as to blade angles and with a moderatel low s ed of rotation. Ir the compressors own t e rotor blade speeds from B to C are constant and the rotor blades are so arranged that compression takes place in these blades as indicated Figs. 3 and 4. vThe guide tially constant.

blades on the casing may be so arranged that a certain amount of .compression is also effected in the guides. It is referred however to emplo in this art of t e com ressor the feature a ady re erred to, name y the feature 0f effecting substantially all the compression in the moving blades. In such case the ide blades may be arranged as indicateduinFigs. 3 and 4 so-that the cross-sec'- tional area at right angles tothe direction of flow between ad'acent blades is substanrom ,B to C the axial clear crossfsectional area of thev rotor blade passages in each stage varies from the inlet `to the outlet side of the blades and in case the axial velocit is to be the same at the inlet and outlet side of the blades as is most desirable, then the axial clear cross-sectional area should be less at the outlet than it is at the inlet side of the blades. The decrease in axial clear cross-sectional area ma be effected b varying the radial depth o` the blades orV y roperly shaping the blades as indicated in 3. and 4. The arrangement and construction of the blades from B to C is such that the fluid is compressed while the absolu-te velocity remains substantially the same at successive stages.

T e fluid discha ed from the last series of rotor blades 12 is rected b livery guide blades 13 to a .c mber 14--from which it passes through the `pipe 8 to a chamber 15 within the casing 7. Thatv part of the compressor between the points D and lE is substantiall .a continuation of the part from B to C an the blades jon the rotor and cas' vare referably .arr edinthe manner descnrib P mi ed in connection wit thel art B to C and-indicated in 5. From to F the mean blade s d in successive stages decreases somew at. pressor the absolute and axial velocities of the uid are decreased somewhat and the rotor and guide blades are preferably 'so arranged t at part of .the compression takes lace in the guides and a art in the rotor lades. The reduction o the velocity in the guide blades causes the Huid to enter the lower speed rotor blades at the proper value for the use of desirable blade angles. At E nearly the'required amountof compression has been effected and from E to G the velocityx'of the fiuid is reduced in order to give a lower rate ofdischarge from the compressor.

From F to G there is' a progressive reduction in the rotor blade speeds in successive blades. Thisisaceo stasand there is also a pro ive increase in t e cross sectional area o the blade passages both in each stage and -in successive stages. The blades are so arranged and constructed from F to G that compression is effected in both the rotor blades and guide lished by `so designing the blades that the/cross sectional area of the passages between the blades'- of each stage aseries of dethe delive In this part of the com both on the rotor and on the casing increase from the entrance to the outlet side of the blades. Compression is therefore effected in both the blades and the guides while the veloc-ity is decreased. By also decreasing theblade velocity in successive stages the fluid is .delivered to each series of rotor blades at such .a velocity with relation to the velocity of the blades as to enable the use of the most desirable and eflicient blade a les.

The amount of lincrease cross sectional .areavof the blade passages from F to G depends u the results which it is desired to accom ish. The larger the reduction in velocity esired the greater the increase of the cross sectional area -of the blade passages. increase in cross sectional area may be effected in an desired manner but is preferably effected y lengthening the blades and 'guides radially in thev manner indicated in i 1 .and also va ing the distance between ad] acent blade su aces as indicated in Fig. 6. The distribution of the rotor blades and conse uently lof the stages between the drums 1 anlil 2 should be so proportioned that the end thrust due to the action of the 'fluid upon the blades of one drum will counterbalance the end thrust due to the action of the fluid upon the blades ofthe other drum.

The fluid .discharged from the last series of blades 16 on the drum 2 is directed by guide blades 17 into a chamber 18 from which it is delivered through a discharge outlet 19.

The guide blades 13 and 1.7 are preferably so arranged on .the two sides of thediametrical lines through the outlets 8 and 19 that the fiuid from the blades on op osite sides ofthis line will be delivered in the general direction of the outlet. In other Words while guide blades have uniform entrance ang es their exit or outlet angles vary in such manner as to deliver the fluid in the general ldirection of the outlet. This arrangement of the delivery guide blades is diagrammatically illustrated in Fig. 2 which indicates a deve opment of 4the circular series of blades. Y

The entrance es of the guide blades 11 at the inlet end o the drum .1 and the entrance a les of the guide blades 20 at the inlet end :if the .drum 2 may be arranged in a similar manner to the arrangement of the delivery guide blades in cases where the incomm fiuid is delivered through an inlet arraiatone side of the rotor as is the pipe 8.

' e I have described my invention as applied to a turbo com ressor certain features and more espec' `ythose relating to the arrangement of the rotor and stator blades in such manner that substantially all changes in pressure and velocity'r take place in the movingrotor blades, `may be embodied with advanta in turbine motors. In such case the axi clear cross sectional area of the passages between the rotor blades of the passa e 35' rection o flow in a stage shou d be substantially uniform.

In case the axial velocity is to be the same` at the inlet and outlet sides of the vanes as is most desirable, then the axial clear crosssectional area should be greater atthe outlet than it is at the inlet side of the vanes.

In 7, 8 and 9 an arran ment of blades is shown whichis well suitegior use in a turbine motor. blades 21 are so arranged that the cross-sectional area at right angles to the direction of flow between ad'acent blades is substantially constant, while the rotor blades 22 are so arranged that the axial clear cross-sectional areas of the, passages between adjacent rotor blades is greatery at the exit than it is at the entrance side of the blades. In thiscase the increase in the passage area in successive stagles required by reason of the expansionof t e steam may be provided for by va g the length of the rotor blades from side-into side in each stage as indicated in F' 8 or as indicated in 9 or may be proviled for in any other sultable manner. If provided for in either of the ways shown the variation in the perrendicular distance between the adjacent b ade surfaces should be such that the axial clear cross sectional area between the blades is greater at the exit tan at the entrance side of the blades.

Substantially the construction above described may be employed as a turbo-pump for acting upon water or other liquids, the angles of the blades bein modified to suit the conditions under whic the construction is to be used. In this case the absolute velocity of the water or other liquid will be increased in the rotor blades and will remain substantially constant throu h the followin ide blades. From A-B t e velocity wi e built up as in the case of the compressor, the liquid being taken in Where the ,blade velocity is comparatively. low and the veloc` ity being built up in t eesuccessive sta es to the point where the blade velocity is t e eatest. From C to D and D to V`E the lades will beso constructed that the velocity of the liquid is increased. In case a moderate velocity of discharge is desired the increase in the cross sectional area of the blade pass es from E to F will be moderate.

When itis desiredI to forcefthe liquid forward against a hi h pressure the increase in the cross section area of the blade passages is made large enough to reduce the velocit e gradually and consequently produce a hi ressure to cause t e forward flow' of the iquid.

As here shown the stator` sively increase the velocity and An arrangement and form of blade suitable for a liquid pump is indicated in Fig. 10. As here shown the .guide blades and.' rotor blades at one sta e from B to C sa at B, are shown at 23,an 24, while the b ades at a later stage say at C, are shown at 25 and 26.

Without attempting to point out indetail the various forms and constructions in which the invention may be embodied, what I claim 1s 1. A turbo-pump provided at its inlet end with radially extending rotor and stator blades arranged in successive sexies axially, the rotor blades being so arranged that the axial clear cross'sectional area between the v blades in each stage varies and the outlet angles decrease in successive stages to progrespressure of the entering fluid in the successivestages, substantially as described.

2. A turbo-pump provided at its inlet end with radially extending stator blades and intermediate radially extending rotor blades arranged in successive series axially and at progressively increasing yradial distances om the axis of the rotor, and with non-increasing inlet and decreasing outlet rotor blade angles in' its successive stages, substantialljT as escribed. y

3. A turbo'pump comprising a rotor having at its inlet end a periphery of increasin diameter, radial blades on the rotor arrange in successive series axially and withnon-increasing inlet and decreasing outlet blade angles in successive series, and a stator provided with intermediate series of blades, substantially as described. e 4. A turbo-pump provided at its inlet end with series of rotor blades having increasing velocities in successive stages, the blades in each stage being so arra ed that @the passages between adjacent b ades 'decrease in axial clear cross sectional area from entrance to exit, and a stator provided with intermediate blades, the bla-des i-n each stage being so arranged thatthe passage between adjacent b lades is substantially uniform in cross sectlonal area at right angles to the flow, sub-` stantially as described.

5. A turbo-pumpprovided at its inlet end with series of rotor blades having increasing velocities in the successive stages, and series of rotor bladeshaving uniform velocit in successive stages, substantially as descri ed.

6. A turbo-pulnp provided at its inlet end with series of rotor blades having increasing velocities lin successive sta es, the blades in each stage being so arrange that the passages between adjacent blades decrease in axial clear cross-sectional area from entrance to exit, a stator provided with intermediate blades, the blades in each stage being so arra ed that the assage between adjacent bla es is substantially uniform in cross sec-.-

tional area at ri ht angles to the ilow, series of` rotor blades avin uniform velocity in successive stages, an intermediate stator blades, substantially as described.

7. A turbo-pump provided at its inlet end with series of rotor blades having increasing velocities in successive stages, series of rotor blades havi uniform velocity in successive stages the b ades in each stage being so arranged that the passa es between adjacent bla es decrease in axia clear cross sectional area from entrance to exit, and a stator provided with blades intermediate the rotor blades, the blades inleach stage beingfso arranged that the passage between adjacent 4 blades is substantially uniform in cross sectional area at right angles to the How, substantially as described.

8. A turbo pump provided at its delivery end with successive series of rotor and stator blades arranged with progressively increas-l ing axial clear area in successive stages to progressively increase the ressure and decrease the velocity of the flui passing through the blades, substantially as described.

9. A turbo-pump provided Aat its delivery end with series of rotor blades arra ed at decreasing distances from the axis of t e rotor and with increasing area for passage of the fluid in the successlve' series, and series of stator blades intermediate successive series of rotor blades, substantially as described.

10. A turbo-pump provided at its delivery i end with series of rotor blades having decreasing velocity in successive st es, series of stator blades intermediate t e rotor blades the blades in each series being so arranged that passage between adjacent blades increases in sectional area from entrance to exit, substantially as described.

11. A turbo pump provided at its inlet end with series of rotor and stator blades constructed and arranged to progressively increase the velocity of theentering fluld 1n.

the successive stages, series of rotor and stator blades constructed and arranged .to

progressively increase the pressure while maintaining a substantially uniform velocity in the successive stages, and series of rotor and stator blades at the delivery end constructed and arranged to progressively decrease the velocity -while increasing -the pres-y sure, substantially. as described.-

12. A turbo ump com rising a rotor pro-4 55 vided at its i et end wit radial blades Varranged in successive series axially, the successlve series being at increasin distances from the axis of the rotor and wit the outer ends of the blades at increasing distances e0 from the axis of the rotor, and a stator provided with intermediate series of radial blades, substantially as described.

13. The combination with a rotor provided with series of blades adjacent yblades in each series being separated by an intervening passage of varying cross sectional area, of a stator provided with intermediate series of blades, adjacent blades in each series being separated by an intervening passage of substantially uniform cross sectional area whereby substantiall all changes in velocity and pressure take p ace in the rotor blades, substantiall as described. v

14. e combination with a rotor rovided with series of radially exten ing blades, adjacent blades in each series being separated by an intervening passage of varying cross sectional area, a stator provided with intermediate series of blades adjacent blades in each series being separated b an intervening passage of substantially un' orm cross sectional area, whereby substantially all changes in velocity and pressure take place in the rotor blades, substantially as described.

. 15. A turbo-pump provided with delivery guide blades having uniform entrance angles and var 'ng exit angles arranged to direct the disc arging fluid` in the same general direction, substantially as described.

16. A turbo-pump rovided with delivery guide blades having 4eir outlet surfaces inclined in the same general direction on the two sides of a diametricalline whereb the air delivered from the two sides of sai line Vis delivered in the same general direction, substantially as described.

In Witness whereof, I have hereunto set my hand, this 24th dacy of January 1907.

y UY B. COLLIER.. In the presence of` l IRA L. FISH,

KA'rnAmNE A, DUGAN. 

